In order to effectively control the flying attitude and integrity of the rod-type killing element,combined with the rotation mechanism of the rod-type killing element,the influence of the oblique angle on the flying posture of the rod-type killing element was analyzed,and a product design method that can control the flying posture of the rod-type killing element was obtained.Combining the theoretical analysis and simulation calculation of the integrity of the rod-type killing element,by adjusting the pressure distribution and energy distribution on the rod-type killing element,the velocity vector distribution on the rod-type killing element is improved,and the deformation of the rod-type killing element is reduced,the rod-type killing element integrity control method was carried out.The rod-type killing element controllable flying test was carried out to verify the effectiveness of the rod-type killing element flying attitude and integrity control method.

With the rapid development of near space hypersonic vehicle,tracking and prediction technology of near space target has attracted wide attention.The main tracking and prediction technologies of near space target are discussed,such as the model of near space hypersonic maneuvering target,the design method of multi-model filter,the trajectory prediction method of near space hypersonic maneuvering target,etc.The main problems of existing methods are pointed out,and the main research directions are given.

Firstly, a complete mathematical description of target missile relative motion problem, which consider the slope error of seeker radome is established,including nonlinear state equation and measurement equation.Secondly,the simplified mathematical model of target missile relative motion considering radome error slope in the elevation channel isgiven,and the mathematical model of joint estimation of line-of-sight rate and radome error slope in the elevation channel is derived.The observability of the joint observation system of line-of-sight rate and radome error slope corresponding to the above mathematical model is proved.Finally,an extended Kalman filter is designed to estimate the line-of-sight rate and radome error slope in the elevation loop and azimuth loop,respectively.The filters are applied in the simulation experiments and compared with the Kalman filter of line-of-sight rate estimation without considering the error slope of radome.The simulation results show that the extended Kalman filter with joint estimation of line-of-sight rate and radome error slope is effective,since it can significantly improve the guidance accuracy of a guidance system with radome error slope.

To make missiles have the ability to generate large overloads quickly when intercepting the high speed maneuvering targets, presents a dual control method of lateral thrust and aerodynamic force. This method can rapidly establish the angle of attack of missiles through a large attitude control moment. The influence of lateral thrust on overload response capability of missile is calculated using theoretical methods. The overload response capability of aerodynamic control and dual control is compared and analyzed. Simulation results show that it′s difficult to improve the response speed of the system by aerodynamic control. The overload response speed of the system can be improved significantly using the dual control of large attitude control moment, so as to achieve the optimal control effect.